Turbomachine including a component having a trench

Abstract

A turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a shroud mounted in one of the compressor portion and the turbine portion. The shroud includes a radial outer side, and a plurality of side surfaces. The radial outer side includes a recessed portion. A trench is formed in the recessed portion, and a cooling passage extends between the trench and at least one of the plurality of side surfaces. An airfoil component is arranged in the one of the compressor portion and the turbine portion. The airfoil component includes an airfoil portion having at least one mounting member. The at least one mounting member includes an internal cavity. A trench element is formed in the internal cavity, and a cooling passage element extends between the trench element and an external surface of the nozzle.

What is claimed is: 
     
         1 . A turbomachine comprising:
 a compressor portion;   a turbine portion operatively connected to the compressor portion;   a shroud mounted in one of the compressor portion and the turbine portion, the shroud including a radial inner side, a radial outer side arranged opposite the radial inner side, and a plurality of side surfaces joining the radial inner side and the radial outer side, the radial outer side including a recessed portion;   at least one trench formed in the recessed portion;   at least one cooling passage extending between the at least one trench and at least one of the plurality of side surfaces;   an airfoil component arranged in the one of the compressor portion or the turbine portion, the airfoil component including an airfoil portion having at least one mounting member, including an internal cavity, the at least one mounting member including a plurality of side surface portions;   at least one trench element formed in the internal cavity; and   at least one cooling passage element extending between the at least one trench element and the one of the plurality of side surface portions.   
     
     
         2 . The turbomachine according to  claim 1 , wherein the plurality of side surfaces includes an upstream side surface, a downstream side surface, a first circumferential side surface and a second circumferential side surface, the plurality of cooling passages extending from the at least one trench to at least one of the first and second circumferential side surfaces. 
     
     
         3 . The turbomachine according to  claim 2 , wherein the at least one trench includes a first trench extending along the first circumferential side surface and a second trench extending along the second circumferential side surface, wherein, the plurality of cooling passages includes a first plurality of cooling passages extending between the first trench and the first circumferential side surface and a second plurality of cooling passages extending between the second trench and the second circumferential side surface. 
     
     
         4 . The turbomachine according to  claim 1 , wherein the shroud is mounted in a turbine portion of a turbomachine. 
     
     
         5 . The turbomachine according to  claim 1 , wherein the plurality of side surface portions include an upstream end, a downstream end, a first circumferential side portion and a second circumferential side portion, the at least one trench being formed at the downstream end of the at least one mounting member. 
     
     
         6 . The turbomachine according to  claim 1 , wherein the airfoil component comprises a nozzle including a first mounting member having a downstream end and a second mounting member having a downstream end, the first mounting member including a first internal cavity having first trench and the second mounting member including a second internal cavity having a second trench, the first trench being formed at the downstream end of the first mounting member and the second trench being formed at the downstream end of the second mounting member. 
     
     
         7 . The turbomachine according to  claim 1 , wherein the at least one cooling passage comprises a plurality of cooling passages extending from the at least one trench to the one of the plurality of side surface portions. 
     
     
         8 . The turbomachine according to  claim 1 , wherein the at least one trench includes a plurality of trenches extending along the one of the plurality of side surface portions. 
     
     
         9 . A turbomachine shroud comprising:
 a radial inner side;   a radial outer side arranged opposite the radial inner side, the radial outer side including a recessed portion;   a plurality of side surfaces joining the radial inner side and the radial outer side;   at least one trench formed in the recessed portion; and   at least one cooling passage extending between the at least one trench and at least one of the plurality of side surfaces.   
     
     
         10 . The turbomachine shroud according to  claim 9 , wherein the plurality of side surfaces includes an upstream side surface, a downstream side surface, a first circumferential side surface and a second circumferential side surface, the plurality of cooling passages extending from the at least one trench to at least one of the first and second circumferential side surfaces. 
     
     
         11 . The turbomachine shroud according to  claim 9 , wherein the at least one trench includes a first trench extending along one of the plurality of side surfaces and a second trench extending along another of the plurality of side surfaces, wherein, the plurality of cooling passages includes a first plurality of cooling passages extending between the first trench and the one of the plurality of sides surfaces and a second plurality of cooling passages extending between the second trench and the other of the plurality of side surfaces. 
     
     
         12 . The turbomachine shroud according to  claim 9 , wherein the radial outer side includes a plurality of recessed portions. 
     
     
         13 . The turbomachine shroud according to  claim 12 , wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another of the opposing ones of the plurality of side surfaces, the first and second trenches being arranged in the upstream end portion. 
     
     
         14 . The turbomachine shroud according to  claim 12 , wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another of the opposing ones of the plurality of side surfaces, the first and second trenches being arranged in the downstream end portion. 
     
     
         15 . The turbomachine shroud according to  claim 12 , wherein the at least one trench includes a first trench arranged along one of the opposing ones of the plurality of side surfaces and a second trench arranged along another the opposing ones of the plurality of side surfaces in the upstream end portion and a third trench arranged along the one of the opposing ones of the plurality of side surfaces and fourth trench arranged along the another of the opposing ones of the plurality of side surfaces in the downstream end portion. 
     
     
         16 . A turbomachine airfoil component comprising:
 an airfoil portion having at least one mounting member including an internal cavity, the at least one mounting member including a plurality of side surface portions;   at least one trench element formed in the internal cavity; and   at least one cooling passage element extending between the at least one trench element and one of the plurality of side surface portions.   
     
     
         17 . The turbomachine nozzle according to  claim 16 , wherein the plurality of side surface portions includes an upstream end, a downstream end, a first circumferential side portion and a second circumferential side portion, the at least one trench being formed at the downstream end of the at least one mounting member. 
     
     
         18 . The turbomachine nozzle according to  claim 16 , wherein the airfoil component comprises a nozzle including a first mounting member having a downstream end and a second mounting member having a downstream end, the first mounting member including a first internal cavity having first trench and the second mounting member including a second internal cavity having a second trench, the first trench being formed at the downstream end of the first mounting member and the second trench being formed at the downstream end of the second mounting member. 
     
     
         19 . The turbomachine nozzle according to  claim 16 , wherein the at least one cooling passage element comprises a plurality of cooling passages extending from the at least one trench to the one of the plurality of side surface portions. 
     
     
         20 . The turbomachine nozzle according to  claim 17 , wherein the at least one trench includes a plurality of trenches extending along the one of the plurality of side surface portions. 
     
     
         21 . A turbomachine component comprising:
 a plurality of surfaces that define an internal cavity;   at least one trench formed in the internal cavity; and   at least one cooling passage extending between the at least one trench and at least one of the plurality of surfaces.   
     
     
         22 . The turbomachine component according to  claim 21 , wherein the plurality of surfaces includes a first circumferential side surface and a second circumferential side surface, the at last one trench extending along one of the first and second circumferential side surfaces. 
     
     
         23 . The turbomachine component according to  claim 22 , wherein the at least one cooling passage extends from the at least one trench to the at least one of the first and second circumferential side surfaces. 
     
     
         24 . The turbomachine component according to  claim 22 , wherein the plurality of surfaces includes an upstream side surface, and a downstream side surface, the at least one trench extending along one of the upstream side surface and the downstream side surface. 
     
     
         25 . The turbomachine component according to  claim 24 , wherein the at least one trench extends along the downstream side surface. 
     
     
         26 . The turbomachine component according to  claim 25 , wherein the at least one cooling passage extends between the at least one trench and the downstream side surface.